ES2391102A1 - Joining arrangement for two boxes of composite material with an intermediate part and method for producing said intermediate part - Google Patents

Abstract

Joining arrangement for two boxes (11, 11') of composite material with an intermediate part (31) and method for manufacturing said intermediate part (31). The joint is effected using rivets between the skins (15, 15' 17, 17') of said boxes (11, 11') and the upper and lower flanges (33, 35) of said T-shaped part (31). The manufacturing method includes the following steps: a) Providing two C-shaped preforms (41, 41'), configured such that their central sections (43, 43') are parallel with one another and their upper and lower flanges (55, 55' 57, 57') are approximately parallel to the end zones of said skins (15, 15' 17', 15') b) Providing two flat preforms (45, 47) to reinforce the flanges (35, 37) c) Forming and curing the part (31) made from said preforms (41, 41', 45, 47) using an RTM method.

Description

PROVISION OF JOINT OF TWO DRAWERS OF COMPOSITE MATERIAL WITH AN INTERMEDIATE PART AND MANUFACTURING PROCEDURE OF SUCH INTERMEDIATE PART

5

FIELD OF THE INVENTION

1st

The present invention relates to an arrangement for joining two drawers of composite material with an intermediate piece and to the method of manufacturing said intermediate piece and in particular to an arrangement for joining the lateral drawers of a horizontal stabilizer of an aircraft with a intermediate piece in the shape of double T.

BACKGROUND OF THE INVENTION

15 2 or 2 5 3 or

At present and particularly in the aeronautical industry, composite materials of organic matrix and continuous fibers are mainly used mainly based on epoxy resins and carbon fibers in a wide variety of structural elements. Aeronautical structures require, as is well known, the integration of various structural elements. For example, fuselages require the integration of coatings with various structural elements such as beams, frames or stringers. Unlike what happened when metal materials were used in which there was practically only the option of mechanical joints for the integration of the various structural elements of a given component, the composite materials allow that integration can also be carried out by chemical joints. In certain aeronautical structures, the union of two components must be done in such a way that an efficient transmission of the load between both components takes place, which usually requires the use of intermediate parts. That happens particularly in the case of the union of the drawers

sides of a horizontal stabilizer of an aircraft since the

Horizontal tail stabilizer should behave as a structural unit.

On the other hand it is a union subject to both aerodynamic loads

as to the loads derived from the mechanism used for trimming the

5

horizontal stabilizer

Being a problematic union, different proposals are known

both cutting joints and tensile joints and using parts

intermediates of metallic, composite or mixed materials.

In one of these proposals, described in US 2009159742, a

1st

intermediate piece in composite material with double T shape.

The use of intermediate parts in the form of double T described in that

document can be problematic for certain drawer configurations

lateral and the present invention is oriented to the solution of those

problems.

fifteen

SUMMARY OF THE INVENTION

It is an object of the present invention to provide an arrangement of

union between two torsion drawers, such as the side drawers of a

2nd

horizontal tail stabilizer of an aircraft, using a piece

double T-shaped intermediate that facilitates the assembly of parts for

realization of said union.

It is another object of the present invention to provide a method of

manufacture of said intermediate piece that allows it to have a configuration

2 5

optimal for its function as an intermediate connecting piece of said drawers

lateral.

In a first aspect, those and other objects are achieved through a

manufacturing procedure for a double T-shaped piece with a soul and

upper and lower wings used as intermediate connecting piece of two

3rd

   structural components shaped like a drawer, including coverings

upper and lower, said union being made between the coatings

upper and lower of said components and the upper and lower wings of

said piece, said piece and said drawers being made in

composite material, comprising the following steps:

-a) Provide two C-shaped preforms, configured so

5

may their souls be parallel to each other and their upper and lower wings be

substantially parallel to the final areas of said coatings.

-b) Provide two flat wing reinforcement preforms.

-e) Conform and cure the piece from these preforms by means of a

RTM procedure.

10

In preferred embodiments, said flat preforms are arranged in

a central area of the wings of the intermediate piece in the form of double T without

extend across its entire width with two or more staggered segments toward your

longitudinal axis. This achieves an effective procedure for the

manufacture of a double T-shaped intermediate piece that facilitates the

fifteen

gradual transfer of loads between drawers.

In other preferred embodiments, said flat preforms comprise

local areas of reinforcement at one of its ends. You get with it a

efficient process for manufacturing a double-shaped intermediate piece

T properly configured for receiving local loads such

2nd

such as loads derived from stabilizer trim mechanisms

tail horizontal

In other preferred embodiments, the intermediate connecting pieces are

apply to drawers with or without dihedral and multi-rib or multi-stringer drawers. Be

this achieves an effective procedure applicable to manufacturing a

2 5

double T-shaped intermediate piece configured appropriately for

The basic types of side drawers of horizontal glue stabilizers

aircraft

In a second aspect, the mentioned objects are achieved

providing a joining arrangement of two structural components

3rd

   drawer-shaped comprising a top liner, a liner

bottom, using an intermediate joint piece with a double T shape and

the connection being made between the coatings of said components and the

upper and lower wings of said piece by rivets, being made

both said part and said components in composite material, in which

said part is manufactured according to the mentioned procedure.

5

In a preferred embodiment, in said joining arrangement they are used at

minus two rows of rivets in each area of different thickness of the wings

top and bottom of the piece. This achieves a joint arrangement

Very effective for transferring loads between drawers.

Other features and advantages of the present invention are

1st

will follow from the detailed description that follows of an embodiment

illustrative of the object of the invention in relation to the attached figures.

DESCRIPTION OF THE FIGURES

fifteen

Figure 1 shows a joining arrangement of two lateral drawers

of a horizontal tail stabilizer of an aircraft with a part

T-shaped intermediate known in the art.

Figure 2 shows a T-shaped intermediate piece according to the

present invention and Figure 3 the preforms used in the process of

2nd

of manufacturing that intermediate part according to the present invention.

Figure 4 shows a cross-sectional view of an arrangement

of union of two lateral drawers with dihedral of a horizontal stabilizer of

tail of an aircraft with a T-shaped intermediate piece according to the

present invention

2 5

Figure 5 shows a cross-sectional view of an arrangement

of union of two lateral drawers without dihedral of a horizontal stabilizer of

tail of an aircraft with a T-shaped intermediate piece according to the

present invention

DETAILED DESCRIPTION OF THE INVENTION

We will now describe embodiments of the invention for case 11 'and, on the other hand, to facilitate a gradual transfer of the load in the

of a joining arrangement of two lateral drawers 11, 11 'of a stabilizer

horizontal tail of an aircraft with a double-shaped intermediate piece

T. Both the 11, 11 'side drawers and the intermediate piece are made

5

with a plastic reinforced carbon fiber composite (CFRP).

In the case of the joint arrangement described in US 2009159742 you can

see, following Figure 1, which is based on the overlap of the wings 25, 27 of

the piece 21 in the form of a double T with the end areas of the coverings 15,

17; 15 ', 17' of the side drawers 11, 11 ', to facilitate a riveted joint

1st

between them. On the other hand, that joining arrangement allows the assembly of

the structure is carried out by positioning the side drawers 11 in place,

11 'and subsequently inserting part 21 between them.

This joint arrangement requires a flattening of the final areas of the

coatings 15, 17; 15 ', 17' so that they sit on the flat wings 25, 27 of

fifteen

the piece.

According to a preferred embodiment of the present invention the arrangement

of joint of two lateral drawers 11, 11 'of a tail stabilizer of a

aircraft with an intermediate piece 31 in the form of a double T, with a soul 33 and

Two wings 35, 37 as shown in Figure 2, is based on the manufacture of

2nd

the part by means of an RTM procedure ("Res in Transfer Molding"), that is

a closed molding process, with resin injection using preforms

shown in Figure 3: two C-shaped preforms 41, 41 ', with souls 43,

43 'and wings 55, 57; 55 ', 57' and two flat preforms 45, 47 (as well

the person skilled in the art will understand the term "flat" should not be understood

2 5

in its strictly geometric sense).

As illustrated in Figures 4 and 5, the intermediate part 31 manufactured

according to said procedure, using appropriate molds, for,

respectively, 11, 11 'drawers with and without dihedral, have wings 35, 37

resulting from the union of the wings 55, 55 '; 57, 57 'of the preforms in C with the

3rd

   flat preforms 45, 4 7 that are specifically configured, on the one hand,

to adapt to the particular configuration of the ends of the drawers 11,

Union.

The aforementioned adaptability of part 31 to the configuration of the

Drawer ends 11, 11 'allows the present invention to be applicable

5

to drawers with or without dihedral as well as to multi-rib or multi-stringer drawers.

On the other hand, and in particular reference to Figures 3 and 4, you can

it is seen that the preforms 45, 47 can be configured with different segments

thickness both longitudinally and transversely.

Thus it can be seen, in Figure 3 that the upper preform 45 comprises

1st

a base segment 61 on which the segment 63 that extends is located

longitudinally over the entire upper wing but having a smaller width

that segment 61, on which, in turn, segments 65 and 67 are located in

One of its ends. With this configuration, on the one hand, the

gradual transfer of loads between drawers 11, 11 'thanks to the

fifteen

stepping of segments 61, 63 and, on the other, a reinforcement is provided

local with segments 65, 67 that may be necessary.

In Figure 4 the upper preform 45 comprises a base segment 61

which does not extend over the entire upper wing of piece 31 - which

it supposes that the first rows of rivets are applied to the union of the

2nd

coatings 15, 15 'and the areas from 55, 55' of the preforms

in C-y segments 63, 65 and 67 of

decreasing width With this staggered configuration the

gradual transfer of loads between drawers 11, 11 'through the piece

31. Figure 4 shows a preferred embodiment with two rows of

25

Rivets 81 in each zone of different thickness.

Among others, the present invention has the following advantages:

-The number of pieces involved in

the junction of drawers 11, 11 '.

-The inner faces 55, 55 '; 57, 57 'of intermediate piece 31 in

30

   contact with the liners 15, 15 ', 17, 17' of the side drawers have,

using an appropriate tool, an optimal finish, which facilitates compliance with

the

requirements of tolerances manufacturing Y mounting, that be makes

by moving the intermediate piece 31, once the drawers

11, 11 'sides are positioned in place, without any subsequent movement

of drawers 11, 11 '.

s

Although the present invention be has described entirely in Connection

with

preferred embodiments, is obvious that be you can enter those

modifications within your

scope, not considering this as limited by

the

previous realizations, if not by he content from

the

following.

10

Claims (6)

1.-Procedure for manufacturing a piece (31) with a double T shape

with a soul (33) and upper and lower wings (35, 37), used as a piece

5

intermediate connection of two structural components (11, 11 ') shaped

drawer, comprising top coverings (15, 15 ') and coverings

lower (17, 17 '), said union being made between the coatings

upper and lower (15, 15 '; 17, 17') of said components (11, 11 ') and the

upper and lower wings (35, 37) of said piece (31), both being made

1st

said piece (31) as said drawers (11, 11 ') in composite material,

characterized in that it comprises the following steps:

-a) provide two C-shaped preforms (41, 41 '), configured from

so that their souls (43, 43 ') are parallel to each other and their upper wings and

lower (55, 55 '; 57, 57') are substantially parallel to the end zones of

fifteen

said coatings (15, 15 '; 17', 15 ');

-b) provide two flat preforms (45, 47) for wing reinforcement

(35, 37);

-e) forming and curing the part (31) from said preforms (41, 41 ',

45, 47) by an RTM procedure.

twenty

2.-Procedure for manufacturing a piece (31) with a double T shape

according to claim 1, characterized in that said flat preforms (45,

47) are arranged in a central area of the wings (35, 37) of the piece (31) without

spread across its width.

25

3.-Procedure for manufacturing a piece (31) with a double T shape

according to claim 2, characterized in that said flat preforms (45,

47) comprise at least two segments (61, 63; 71, 73) of different thickness,

having the thickest segments (63, 73) smaller than the

3rd

thinner segments (61, 71).

4. Method of manufacturing a double T-shaped part (31) according to claim 3, characterized in that said flat preforms (45, 4 7) comprise local reinforcement zones at one of their ends.

5

5. Method of manufacturing a double T-shaped part (31) according to any of claims 1-4, characterized in that the end areas of the coverings (15, 17; 15 ', 17') of said drawers (11 , 11 ') are not parallel to each other.

1st

6. Process for manufacturing a double T-shaped part (31) according to any of claims 1-4, characterized in that the end areas of the coverings (15, 17; 15 ', 17') of said drawers (11 , 11 ') are parallel to each other.

fifteen

7. Method of manufacturing a double T-shaped part (31) according to claim 6, characterized in that the final areas of the upper coverings (15, 15 ') and the lower coverings (17, 17') of said drawers (11, 11 ') are not aligned with each other.

2nd

8. Method of manufacturing a double T-shaped part (31) according to any one of claims 1-7, characterized in that said drawers (11, 11 ') are multi-rib drawers.

2 5

9. Method of manufacturing a piece (31) in the form of a double T according to any of claims 1-7, characterized in that said drawers (11, 11 ') are multi-stringer drawers.

3rd

   10. Method of manufacturing a double T-shaped part (31) according to any of claims 1-9, characterized in that said drawers (11, 11 ') are the side drawers of a horizontal tail stabilizer of an aircraft.

11.-Joint arrangement of two structural components (11, 11 ') with

shape

from drawer understanding a coating higher (fifteen, fifteen'), a

bottom lining (17, 17 '), using

a intermediate connecting piece (31)

5

with a double T shape and the joint between the coatings being made (15, 15 ';

17, 17 ') of said components (11, 11') and the upper and lower wings (33, 35)

of said piece (31) by rivets, said piece being made both

(31) as said components (11, 11 ') in composite material, characterized

because said part (31) is manufactured according to the procedure object of any of

1st

claims 1-1 O.

12.

Provision from Union according the claim 11, characterized

because at least two rows of rivets are used (81)

in each zone of different

thickness of the upper and lower wings (33, 35) of the piece (31).

fifteen